EP3752420A1 - De-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle - Google Patents

De-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle

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Publication number
EP3752420A1
EP3752420A1 EP19710043.1A EP19710043A EP3752420A1 EP 3752420 A1 EP3752420 A1 EP 3752420A1 EP 19710043 A EP19710043 A EP 19710043A EP 3752420 A1 EP3752420 A1 EP 3752420A1
Authority
EP
European Patent Office
Prior art keywords
acoustic
deicing
cells
air
cell
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP19710043.1A
Other languages
German (de)
French (fr)
Other versions
EP3752420B1 (en
Inventor
Virginie Emmanuelle Anne Marie DIGEOS
Patrick BOILEAU
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Nacelles SAS
Original Assignee
Safran Nacelles SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Nacelles SAS filed Critical Safran Nacelles SAS
Publication of EP3752420A1 publication Critical patent/EP3752420A1/en
Application granted granted Critical
Publication of EP3752420B1 publication Critical patent/EP3752420B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
    • B64D15/04—Hot gas application
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0206—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising noise reduction means, e.g. acoustic liners
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/06—Attaching of nacelles, fairings or cowlings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/047—Heating to prevent icing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines

Definitions

  • the invention relates to a device for deicing and acoustic treatment for an air intake lip of a turbojet engine nacelle and its manufacturing method.
  • An aircraft is propelled by one or more propulsion units each comprising a turbojet / turboprop engine housed in a tubular nacelle.
  • Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
  • a nacelle generally has a structure comprising an air inlet upstream of the engine, a median section intended to surround a fan of the turbojet, a downstream section housing thrust reverser means and intended to surround the combustion chamber of the turbojet engine, and is generally terminated by an ejection nozzle whose outlet is located downstream of the turbojet engine.
  • the air intake comprises, on the one hand, an air intake lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet, and on the other hand, a downstream structure on which the lip is attached and intended to channel the air towards the vanes of the fan.
  • the assembly is attached upstream of a blower housing belonging to the upstream section of the nacelle.
  • ice can form on the nacelle, particularly at the outer surface of the air intake lip.
  • the presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower.
  • frost formation on the nacelle's air intake and ice ingestion by the engine in the event of ice blocks being detached can damage the engine and pose a risk to the safety of the flight.
  • One solution for de-icing the outer surface of the air inlet lip is to prevent ice from forming on this outer surface by keeping the surface concerned at a sufficient temperature.
  • the acoustic panel comprises a perforated acoustic skin which is arranged opposite the inlet air stream of the nacelle and a cellular core which is assembled on the acoustic skin.
  • the alveolar core comprises a plurality of acoustic cells forming Helmholtz resonators, which are separated from each other by peripheral partitions.
  • the acoustic cells extend in thickness from a front end resting on the acoustic skin, to a rear end closed by a rear face.
  • the cellular core is generally made flat and has a high mechanical resistance to compression and bending, which makes it difficult to shape the acoustic panel, in particular to shape the acoustic panel according to the geometry of a lip air intake of a nacelle.
  • the document WO 2009/081020 describes and represents a structure for the acoustic treatment which makes an acoustic treatment and a treatment of the frost coexist.
  • the structure comprises an acoustic skin, an alveolar core comprising strips of cells, a reflecting skin and a plurality of channels which are interposed between the cells and which are intended to channel hot air from a heating system. defrost.
  • channels and the bands of cells form separate subsets which are manufactured independently and which are assembled together.
  • the cell strips that form the cellular core do not seem to have a high mechanical strength, the honeycomb core is therefore little involved in the mechanical strength of the air intake lip.
  • the design of the channels for the circulation of hot air seems to limit the circulation of hot air and the exchange surface between the hot air and the acoustic skin of the air intake lip.
  • the present invention aims in particular to solve these drawbacks and relates for this purpose to a deicing and treatment device acoustic device for an air intake lip of a turbojet engine nacelle, characterized in that it comprises an embossed acoustic structure which is adapted to bear on an acoustic skin of the air inlet lip, and which delimits a plurality of acoustic cells, each cell being delimited by an independent peripheral wall which allows the circulation of a flow of deicing air around each cell.
  • Embossed acoustic structure is understood to mean a structure having an alternation of raised acoustic cells and lattice-shaped recesses, in which the recesses situated between the cells constitute intersecting lines such as a grid.
  • the device according to the invention allows the defrosting air to circulate around each cell, the acoustic structure which forms the cells transmitting the calories of the defrost air to the acoustic skin by conduction.
  • the acoustic structure delimits at least two rows of cells which are interconnected by at least one connecting portion adapted to bear against the acoustic skin of the air intake lip.
  • This feature increases the contact area between the acoustic structure and the acoustic skin to promote the conduction of calories from the defrost air to the acoustic skin.
  • the cells are made integral with the associated binding portion.
  • each row of acoustic cells has an annular shape around a central axis.
  • the acoustic structure has a monolithic annular shape or a shape of several monolithic angular sectors.
  • This characteristic favors the manufacture of the acoustic structure.
  • each cell has a generally pyramidal shape.
  • the device comprises at least one deflector which is designed to guide a flow of defrost air towards the acoustic structure. This feature improves the heat exchange between the defrosting air and the acoustic structure.
  • the device comprises a defrosting air distribution tube which has a toric shape around the axis and which delimits a plurality of injector slots, the slots being arranged facing the cells to direct the air defrost between the cells.
  • the invention also relates to a method for manufacturing a deicing and acoustic treatment device for an air inlet lip of a turbojet engine nacelle, which device comprises an embossed acoustic structure which delimits a plurality of acoustic cells, each cell being delimited by an independent peripheral wall which allows the circulation of a flow of defrosting air around each cell, characterized in that it comprises at least one manufacturing step which consists in producing the acoustic structure from the material in a monolithic room.
  • the invention also relates to a turbojet engine nacelle of the type comprising a deicing and acoustic treatment device of the type described above.
  • FIG. 1 is a schematic longitudinal sectional view which illustrates a turbojet engine nacelle comprising an air intake lip equipped with a deicing device and acoustic treatment according to the invention
  • FIG. 2 is a cutaway perspective view which illustrates the embossed acoustic structure of the device according to the invention
  • FIG. 3 is a detailed perspective view in longitudinal section which illustrates the embossed acoustic structure of the device according to the invention on the acoustic skin;
  • FIG. 4 is a diagrammatic cross-sectional view illustrating deflectors for guiding deicing air in the lip, according to a first embodiment of the invention
  • FIG. 5 is a diagrammatic cross-sectional view which illustrates a deflector for guiding deicing air in the lip, according to a second variant embodiment of the invention
  • FIG. 6 is a schematic view in longitudinal section which illustrates the deflector of FIG. 5, according to the second variant embodiment of the invention
  • FIG. 7 is a diagrammatic cross-sectional view illustrating a tube for guiding deicing air in the lip, according to a third embodiment of the invention.
  • FIG. 8 is a schematic longitudinal sectional view which illustrates the deflector of Figure 7, according to the third embodiment of the invention.
  • the vertical axis V extends radially generally with respect to the central longitudinal axis A of the nacelle and the transverse axis T extends generally tangentially with respect to the central longitudinal axis A of the nacelle.
  • upstream and downstream must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet engine. that is, from the left to the right of FIG.
  • FIG. 1 shows a nacelle 10 of generally annular shape which extends around a central longitudinal axis A.
  • the nacelle 10 comprises an air inlet 12 upstream of the engine 14, a median section 16 intended to surround a fan 18 of the turbojet, a downstream section 20 housing thrust reversal means and intended to surround the combustion chamber of the engine. turbojet, and an exhaust nozzle 22 whose output is located downstream of the turbojet engine.
  • the air inlet 12 comprises an air inlet lip 24 which forms a volume of annular shape around the central axis A of the nacelle 10, of shaped section. of "D".
  • the air inlet lip 24 is delimited by an upstream upstream defrosting wall 26, forming a leading edge, and a downstream partition 28 which separates the volume defined by the lip 24 of the air intake and the section of the nacelle 10 which is connected to the lip 24.
  • the lip 24 is equipped with a device 30 for defrosting and acoustic treatment which comprises an embossed acoustic structure 32 which bears on a perforated acoustic skin 33 of the lip 24.
  • the acoustic structure 32 has an annular shape around the central axis A of the nacelle.
  • the acoustic structure 32 defines a plurality of acoustic cells 34 arranged in three rows 36 which each extend in a circle about the central axis A.
  • Each cell 34 is delimited by an independent peripheral wall 38 which allows the circulation of a flow of defrosting air around each cell 34.
  • independent peripheral wall means that the adjacent cells 34 do not have a common wall, so that the defrosting air can circulate around each cell 34.
  • each cell 34 has a dome shape.
  • each cell 34 has a pyramidal shape, the peripheral wall 38 of each cell 34 forming four faces which are each in contact with the deicing air flowing in the lip 24.
  • each cell 34 may have a parallelepiped shape, such as a square shape.
  • the three rows 36 are interconnected two by two by two connecting portions 40 which bear on the acoustic skin 33 of the air intake lip 24.
  • Each connecting portion 40 is a band that extends longitudinally in width and which matches the shape of the lip 24.
  • the cells 34 adjacent to each connecting portion 40 form a valley in which the defrosting air flows to transmit heat to the acoustic skin 33 by conduction, via the acoustic structure 32 and particularly via connecting portions 40.
  • each cell 34 is also adapted so that the defrosting air circulates longitudinally between the cells 34, that is to say perpendicularly to the connecting portions 40.
  • the acoustic structure 32 may also comprise connecting strips (not shown) which extend longitudinally in length to connect the cells 34 to each other. This characteristic is particularly suitable for parallelepiped-shaped cells 34 to allow the cells 34 to be moved aside and allow the defrosting air to flow longitudinally between the cells 34.
  • each cell 34 and each connecting portion 40 are formed by the acoustic structure 32 in a monolithic piece.
  • the acoustic structure 32 is made by cold forming by stamping a metal sheet.
  • the acoustic structure 32 can also be achieved by explosion-forming, by incremental forming, by magnetoforming, or by hot forming.
  • the acoustic structure 32 is preferably made of several angular sectors.
  • the acoustic structure 32 is reported and fixed on the acoustic skin 33 perforated, for example by brazing.
  • the sheet used to manufacture the acoustic structure 32 may be co-laminated with a solder alloy to eliminate the step of depositing the solder on the acoustic structure 32.
  • the acoustic structure 32 can also be fixed by welding.
  • the holes 41 formed in the acoustic skin 33 which are arranged at the right of the connecting portions 40 are plugged by the acoustic connection portions 40 and the holes 41 which are arranged in line with the cells 34 are open and open into the cells 34.
  • the device 10 comprises a defrost air distribution tube 42 illustrated in FIGS. 2, 7 and 8, which has a toric shape around the central axis A and which is arranged in the lip 24.
  • the tube 42 has an inlet (not shown) which is connected to a defrost hot air source and an outlet (not shown).
  • the tube 42 defines a plurality of injector slots 44, which are arranged facing the cells 34 and which direct the air defrosting between the cells 34, so that the defrosting air passes around each cell 34 as can be seen in FIGS. 7 and 8.
  • the device 10 comprises a plurality of deflectors 46 which replace the defrosting air distribution tube 42 and which are angularly arranged in a regular manner around the central axis A.
  • the defrosting air is injected into the lip 24 by a nozzle 48 which prints a circular motion to the defrosting air around the central axis A.
  • each deflector 46 covers the acoustic structure 32 and extends generally tangentially with respect to the central axis A, and each deflector 46 has a leading edge 50 which is substantially raised to direct a portion of the air flow defrosting to the cells 34 to promote heat exchange.
  • the device 10 comprises an annular baffle 52 which extends around the central axis A and which surrounds the acoustic structure 32.
  • the defrosting air is injected into the lip 32 via an inlet 54 which is formed in the downstream partition 28, so that the defrosting air swirls in the lip 24 as illustrated by the arrow in Figure 6.
  • the deflector 52 is bent at both ends so that the flow of swirling defrost air passes between the deflector 52 and the cells 34, to promote heat exchange.
  • the invention also relates to a method of manufacturing a device 10 for deicing and acoustic treatment of the type described above, which comprises a manufacturing step which consists in producing the rows 36 of acoustic cells 34 and the associated connecting portions 40 of matter.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention concerns a de-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle, characterised in that it comprises an embossed acoustic structure (32) that delimits a plurality of acoustic cells (34), each cell (34) being delimited by an independent peripheral wall (38) that allows a flow of de-icing air to flow around each cell (34).

Description

DISPOSITIF DE DEGIVRAGE ET DE TRAITEMENT ACOUSTIQUE POUR UNE LEVRE D’ENTREE D’AIR D’UNE NACELLE DE TURBOREACTEUR  DEVICE FOR DEFROSTING AND ACOUSTIC TREATMENT FOR AIR INJECTION LIP OF A TURBOJET NACELLE
L’invention concerne un dispositif de dégivrage et de traitement acoustique pour une lèvre d’entrée d’air d’une nacelle de turboréacteur et son procédé de fabrication. The invention relates to a device for deicing and acoustic treatment for an air intake lip of a turbojet engine nacelle and its manufacturing method.
Un avion est propulsé par un ou plusieurs ensembles propulsifs comprenant chacun un turboréacteur/turbopropulseur logé dans une nacelle tubulaire. Chaque ensemble propulsif est rattaché à l'avion par un mât situé généralement sous une aile ou au niveau du fuselage.  An aircraft is propelled by one or more propulsion units each comprising a turbojet / turboprop engine housed in a tubular nacelle. Each propulsion unit is attached to the aircraft by a mast located generally under a wing or at the fuselage.
Une nacelle présente généralement une structure comprenant une entrée d'air en amont du moteur, une section médiane destinée à entourer une soufflante du turboréacteur, une section aval abritant des moyens d'inversion de poussée et destinée à entourer la chambre de combustion du turboréacteur, et est généralement terminée par une tuyère d'éjection dont la sortie est située en aval du turboréacteur.  A nacelle generally has a structure comprising an air inlet upstream of the engine, a median section intended to surround a fan of the turbojet, a downstream section housing thrust reverser means and intended to surround the combustion chamber of the turbojet engine, and is generally terminated by an ejection nozzle whose outlet is located downstream of the turbojet engine.
L'entrée d'air comprend, d'une part, une lèvre d'entrée d’air adaptée pour permettre la captation optimale vers le turboréacteur de l'air nécessaire à l'alimentation de la soufflante et des compresseurs internes du turboréacteur, et d'autre part, une structure aval sur laquelle est rapportée la lèvre et destinée à canaliser l'air vers les aubes de la soufflante. L'ensemble est rattaché en amont d'un carter de la soufflante appartenant à la section amont de la nacelle.  The air intake comprises, on the one hand, an air intake lip adapted to allow optimal capture to the turbojet of the air necessary to supply the blower and the internal compressors of the turbojet, and on the other hand, a downstream structure on which the lip is attached and intended to channel the air towards the vanes of the fan. The assembly is attached upstream of a blower housing belonging to the upstream section of the nacelle.
En vol, selon les conditions de température et d'humidité, de la glace peut se former sur la nacelle, notamment au niveau de la surface externe de la lèvre d'entrée d'air. La présence de glace ou de givre modifie les propriétés aérodynamiques de l'entrée d'air et perturbe l'acheminement de l'air vers la soufflante. De plus, la formation de givre sur l'entrée d'air de la nacelle et l'ingestion de glace par le moteur en cas de détachement de blocs de glace peuvent endommager le moteur, et présenter un risque pour la sécurité du vol.  In flight, depending on the temperature and humidity conditions, ice can form on the nacelle, particularly at the outer surface of the air intake lip. The presence of ice or frost changes the aerodynamic properties of the air intake and disturbs the flow of air to the blower. In addition, frost formation on the nacelle's air intake and ice ingestion by the engine in the event of ice blocks being detached can damage the engine and pose a risk to the safety of the flight.
Une solution pour dégivrer la surface externe de la lèvre d’entrée d’air consiste à éviter que de la glace ne se forme sur cette surface externe en maintenant la surface concernée à une température suffisante.  One solution for de-icing the outer surface of the air inlet lip is to prevent ice from forming on this outer surface by keeping the surface concerned at a sufficient temperature.
Ainsi, il est connu, par exemple du brevet US 4 688 757, de prélever de l'air chaud au niveau du compresseur du turboréacteur et de l'amener au niveau de la lèvre d'entrée d'air afin de réchauffer la surface externe de la lèvre. Aussi, il est connu d’équiper la lèvre d’entrée d’air de la nacelle d’un panneau acoustique adapté pour absorber une partie du bruit émis depuis l’intérieur de la nacelle vers l’extérieur de la nacelle. Thus, it is known, for example from US Pat. No. 4,688,757, to draw hot air at the compressor of the turbojet engine and to bring it to the level of the air intake lip in order to heat the external surface. of the lip. Also, it is known to equip the air intake lip of the nacelle with an acoustic panel adapted to absorb some of the noise emitted from inside the nacelle to the outside of the nacelle.
Typiquement, le panneau acoustique comporte une peau acoustique perforée qui est agencée en regard de la veine d’entrée d’air de la nacelle et une âme alvéolaire qui est assemblée sur la peau acoustique.  Typically, the acoustic panel comprises a perforated acoustic skin which is arranged opposite the inlet air stream of the nacelle and a cellular core which is assembled on the acoustic skin.
L’âme alvéolaire comporte une pluralité de cellules acoustiques, formant résonateurs de Helmholtz, qui sont séparées entre elles par des cloisons périphériques.  The alveolar core comprises a plurality of acoustic cells forming Helmholtz resonators, which are separated from each other by peripheral partitions.
Les cellules acoustiques s’étendent en épaisseur depuis une extrémité avant en appui sur la peau acoustique, jusqu’à une extrémité arrière obturée par une face arrière.  The acoustic cells extend in thickness from a front end resting on the acoustic skin, to a rear end closed by a rear face.
L’âme alvéolaire est généralement réalisée à plat et présente une grande résistance mécanique à la compression et à la flexion, ce qui rend difficile la mise en forme du panneau acoustique, notamment pour mettre en forme le panneau acoustique suivant la géométrie d’une lèvre d’entrée d’air d’une nacelle.  The cellular core is generally made flat and has a high mechanical resistance to compression and bending, which makes it difficult to shape the acoustic panel, in particular to shape the acoustic panel according to the geometry of a lip air intake of a nacelle.
Le document WO 2009/081020 décrit et représente une structure pour le traitement acoustique qui fait coexister un traitement acoustique et un traitement du givre.  The document WO 2009/081020 describes and represents a structure for the acoustic treatment which makes an acoustic treatment and a treatment of the frost coexist.
Selon ce document, la structure comprend une peau acoustique, une âme alvéolaire comportant des bandes de cellules, une peau réflectrice et une pluralité de canaux qui sont interposés entre les cellules et qui sont destinés à canaliser de l’air chaud d’un système de dégivrage.  According to this document, the structure comprises an acoustic skin, an alveolar core comprising strips of cells, a reflecting skin and a plurality of channels which are interposed between the cells and which are intended to channel hot air from a heating system. defrost.
On notera que les canaux et les bandes de cellules forment des sous ensembles distincts qui sont fabriqués indépendemment et qui sont assemblés entre eux.  It will be noted that the channels and the bands of cells form separate subsets which are manufactured independently and which are assembled together.
La fabrication d’une telle structure s’avère longue et onéreuse. The manufacture of such a structure is long and expensive.
De plus, les bandes de cellules qui forment l’âme alvéolaire ne semblent pas présenter une résistance mécanique élevée, l’âme alvéolaire participe donc peu à la résistance mécanique de la lèvre d’entrée d’air. In addition, the cell strips that form the cellular core do not seem to have a high mechanical strength, the honeycomb core is therefore little involved in the mechanical strength of the air intake lip.
Aussi, la conception des canaux pour la circulation de l’air chaud semble limiter la circulation de l’air chaud et la surface d’échange entre l’air chaud et la peau acoustique de la lèvre d’entrée d’air.  Also, the design of the channels for the circulation of hot air seems to limit the circulation of hot air and the exchange surface between the hot air and the acoustic skin of the air intake lip.
La présente invention vise notamment à résoudre ces inconvénients et se rapporte pour ce faire à un dispositif de dégivrage et de traitement acoustique pour une lèvre d’entrée d’air d’une nacelle de turboréacteur, caractérisé en ce qu’il comporte une structure acoustique gaufrée qui est adaptée pour être en appui sur une peau acoustique de la lèvre d’entrée d’air, et qui délimite une pluralité de cellules acoustiques, chaque cellule étant délimitée par une paroi périphérique indépendante qui permet la circulation d’un flux d’air de dégivrage autour de chaque cellule. The present invention aims in particular to solve these drawbacks and relates for this purpose to a deicing and treatment device acoustic device for an air intake lip of a turbojet engine nacelle, characterized in that it comprises an embossed acoustic structure which is adapted to bear on an acoustic skin of the air inlet lip, and which delimits a plurality of acoustic cells, each cell being delimited by an independent peripheral wall which allows the circulation of a flow of deicing air around each cell.
Par structure acoustique gaufrée on entend une structure présentant une alternance de cellules acoustiques en relief et de creux disposés en réseau, dans laquelle les creux situés entre les cellules constituent des lignes entrecroisées tel un quadrillage.  Embossed acoustic structure is understood to mean a structure having an alternation of raised acoustic cells and lattice-shaped recesses, in which the recesses situated between the cells constitute intersecting lines such as a grid.
Le dispositif selon l’invention permet à l’air de dégivrage de circuler autour de chaque cellule, la structure acoustique qui forme les cellules transmettant les calories de l’air de dégivrage vers la peau acoustique par conduction.  The device according to the invention allows the defrosting air to circulate around each cell, the acoustic structure which forms the cells transmitting the calories of the defrost air to the acoustic skin by conduction.
Selon une autre caractéristique, la structure acoustique délimite au moins deux rangées de cellules qui sont reliées entre elles par au moins une portion de liaison adaptée pour être en appui sur la peau acoustique de la lèvre d’entrée d’air.  According to another characteristic, the acoustic structure delimits at least two rows of cells which are interconnected by at least one connecting portion adapted to bear against the acoustic skin of the air intake lip.
Cette caractéristique augmente la surface de contact entre la structure acoustique et la peau acoustique pour favoriser la conduction des calories de l’air de dégivrage vers la peau acoustique.  This feature increases the contact area between the acoustic structure and the acoustic skin to promote the conduction of calories from the defrost air to the acoustic skin.
Selon une autre caractéristique, les cellules sont réalisées venues de matière avec la portion de liaison associée.  According to another characteristic, the cells are made integral with the associated binding portion.
Selon une autre caractéristique, chaque rangée de cellules acoustiques présente une forme annulaire autour d’un axe central.  According to another characteristic, each row of acoustic cells has an annular shape around a central axis.
Selon une autre caractéristique, la structure acoustique présente une forme annulaire monolithique ou une forme de plusieurs secteurs angulaires monolithiques.  According to another characteristic, the acoustic structure has a monolithic annular shape or a shape of several monolithic angular sectors.
Cette caractéristique favorise la fabrication de la structure acoustique.  This characteristic favors the manufacture of the acoustic structure.
Selon une autre caractéristique, chaque cellule présente une forme globalement pyramidale.  According to another characteristic, each cell has a generally pyramidal shape.
Selon une autre caractéristique, le dispositif comporte au moins un déflecteur qui est conçu pour guider un flux d’air de dégivrage vers la structure acoustique. Cette caractéristique améliore l’échange thermique entre l’air de dégivrage et la structure acoustique. According to another characteristic, the device comprises at least one deflector which is designed to guide a flow of defrost air towards the acoustic structure. This feature improves the heat exchange between the defrosting air and the acoustic structure.
Selon une autre caractéristique, le dispositif comporte un tube de distribution de l’air de dégivrage qui présente une forme torique autour de l’axe et qui délimite une pluralité de fentes formant injecteurs, les fentes étant agencées en regard des cellules pour diriger l’air de dégivrage entre les cellules.  According to another characteristic, the device comprises a defrosting air distribution tube which has a toric shape around the axis and which delimits a plurality of injector slots, the slots being arranged facing the cells to direct the air defrost between the cells.
L’invention concerne également un procédé de fabrication d’un dispositif de dégivrage et de traitement acoustique pour une lèvre d’entrée d’air d’une nacelle de turboréacteur, dispositif qui comporte une structure acoustique gaufrée qui délimite une pluralité de cellules acoustiques, chaque cellule étant délimitée par une paroi périphérique indépendante qui permet la circulation d’un flux d’air de dégivrage autour de chaque cellule, caractérisé en ce qu’il comprend au moins une étape de fabrication qui consiste à réaliser la structure acoustique venue de matière en une pièce monolithique.  The invention also relates to a method for manufacturing a deicing and acoustic treatment device for an air inlet lip of a turbojet engine nacelle, which device comprises an embossed acoustic structure which delimits a plurality of acoustic cells, each cell being delimited by an independent peripheral wall which allows the circulation of a flow of defrosting air around each cell, characterized in that it comprises at least one manufacturing step which consists in producing the acoustic structure from the material in a monolithic room.
L’invention concerne également une nacelle de turboréacteur du type comportant un dispositif de dégivrage et de traitement acoustique du type décrit précédemment.  The invention also relates to a turbojet engine nacelle of the type comprising a deicing and acoustic treatment device of the type described above.
D'autres caractéristiques et avantages de l'invention apparaîtront à la lecture de la description détaillée qui suit pour la compréhension de laquelle on se reportera aux dessins annexés dans lesquels :  Other features and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:
- la figure 1 est une vue schématique en section longitudinale qui illustre une nacelle de turboréacteur comprenant une lèvre d’entrée d’air équipée d’un dispositif de dégivrage et de traitement acoustique selon l’invention ;  - Figure 1 is a schematic longitudinal sectional view which illustrates a turbojet engine nacelle comprising an air intake lip equipped with a deicing device and acoustic treatment according to the invention;
- la figure 2 est une vue en perspective avec arrachement qui illustre la structure acoustique gaufrée du dispositif selon l’invention ;  - Figure 2 is a cutaway perspective view which illustrates the embossed acoustic structure of the device according to the invention;
- la figure 3 est une vue en perspective de détail en section longitudinale qui illustre la structure acoustique gaufrée du dispositif selon l’invention sur la peau acoustique ;  FIG. 3 is a detailed perspective view in longitudinal section which illustrates the embossed acoustic structure of the device according to the invention on the acoustic skin;
- la figure 4 est une vue schématique en section transversale qui illustre des déflecteurs pour le guidage de l’air de dégivrage dans la lèvre, selon une première variante de réalisation de l’invention ;  FIG. 4 is a diagrammatic cross-sectional view illustrating deflectors for guiding deicing air in the lip, according to a first embodiment of the invention;
- la figure 5 est une vue schématique en section transversale qui illustre un déflecteur pour le guidage de l’air de dégivrage dans la lèvre, selon une deuxième variante de réalisation de l’invention ; - la figure 6 est une vue schématique en section longitudinale qui illustre le déflecteur de la figure 5, selon la deuxième variante de réalisation de l’invention ; FIG. 5 is a diagrammatic cross-sectional view which illustrates a deflector for guiding deicing air in the lip, according to a second variant embodiment of the invention; FIG. 6 is a schematic view in longitudinal section which illustrates the deflector of FIG. 5, according to the second variant embodiment of the invention;
- la figure 7 est une vue schématique en section transversale qui illustre un tube pour le guidage de l’air de dégivrage dans la lèvre, selon une troisième variante de réalisation de l’invention ;  FIG. 7 is a diagrammatic cross-sectional view illustrating a tube for guiding deicing air in the lip, according to a third embodiment of the invention;
- la figure 8 est une vue schématique en section longitudinale qui illustre le déflecteur de la figure 7, selon la troisième variante de réalisation de l’invention.  - Figure 8 is a schematic longitudinal sectional view which illustrates the deflector of Figure 7, according to the third embodiment of the invention.
Dans la description et les revendications, on utilisera à titre non limitatif la terminologie longitudinal, vertical et transversal en référence au trièdre L, V, T indiqué aux figures, dont l’axe L est parallèle à l’axe A central de la nacelle.  In the description and the claims, the longitudinal, vertical and transverse terminology will be used in a nonlimiting manner with reference to the L, V, T trihedron indicated in the figures, the L axis of which is parallel to the central axis A of the nacelle.
On notera que l’axe vertical V s’étend globalement radialement par rapport à l’axe A central longitudinal de la nacelle et l’axe transversal T s’étend globalement tangentiellement par rapport à l’axe A central longitudinal de la nacelle.  It will be noted that the vertical axis V extends radially generally with respect to the central longitudinal axis A of the nacelle and the transverse axis T extends generally tangentially with respect to the central longitudinal axis A of the nacelle.
A noter également que dans la présente demande de brevet, les termes « amont » et « aval » doivent s’entendre par rapport à la circulation du flux d’air à l’intérieur de l’ensemble propulsif formé par la nacelle et le turboréacteur, c’est-à-dire de la gauche vers la droite de la figure 1 .  Note also that in the present patent application, the terms "upstream" and "downstream" must be understood in relation to the flow of air flow inside the propulsion unit formed by the nacelle and the turbojet engine. that is, from the left to the right of FIG.
Sur l’ensemble des figures, des références identiques ou analogues représentent des organes ou ensembles d’organes identiques ou analogues.  Throughout the figures, identical or similar references represent identical or similar organs or sets of members.
On a représenté à la figure 1 une nacelle 10 de forme globalement annulaire qui s’étend autour d’un axe A central longitudinal.  FIG. 1 shows a nacelle 10 of generally annular shape which extends around a central longitudinal axis A.
La nacelle 10 comprend une entrée d'air 12 en amont du moteur 14, une section médiane 16 destinée à entourer une soufflante 18 du turboréacteur, une section aval 20 abritant des moyens d'inversion de poussée et destinée à entourer la chambre de combustion du turboréacteur, et une tuyère d'éjection 22 dont la sortie est située en aval du turboréacteur.  The nacelle 10 comprises an air inlet 12 upstream of the engine 14, a median section 16 intended to surround a fan 18 of the turbojet, a downstream section 20 housing thrust reversal means and intended to surround the combustion chamber of the engine. turbojet, and an exhaust nozzle 22 whose output is located downstream of the turbojet engine.
Comme on peut le voir à la figure 2, l'entrée d'air 12 comprend une lèvre 24 d'entrée d’air qui forme un volume de forme annulaire autour de l’axe A central de la nacelle 10, de section en forme de « D ».  As can be seen in FIG. 2, the air inlet 12 comprises an air inlet lip 24 which forms a volume of annular shape around the central axis A of the nacelle 10, of shaped section. of "D".
La lèvre 24 d’entrée d’air est délimitée par une paroi externe 26 amont à dégivrer, formant bord d’attaque, et une cloison aval 28 qui sépare le volume délimité par la lèvre 24 d’entrée d’air et le tronçon de la nacelle 10 qui est relié sur la lèvre 24. The air inlet lip 24 is delimited by an upstream upstream defrosting wall 26, forming a leading edge, and a downstream partition 28 which separates the volume defined by the lip 24 of the air intake and the section of the nacelle 10 which is connected to the lip 24.
La lèvre 24 est équipée d’un dispositif 30 de dégivrage et de traitement acoustique qui comporte une structure acoustique 32 gaufrée qui est en appui sur une peau acoustique 33 perforée de la lèvre 24.  The lip 24 is equipped with a device 30 for defrosting and acoustic treatment which comprises an embossed acoustic structure 32 which bears on a perforated acoustic skin 33 of the lip 24.
La structure acoustique 32 présente une forme annulaire autour de l’axe A central de la nacelle.  The acoustic structure 32 has an annular shape around the central axis A of the nacelle.
Aussi, la structure acoustique 32 délimite une pluralité de cellules 34 acoustiques agencées en trois rangées 36 qui s’étendent chacune en cercle autour de l’axe A central.  Also, the acoustic structure 32 defines a plurality of acoustic cells 34 arranged in three rows 36 which each extend in a circle about the central axis A.
Chaque cellule 34 est délimitée par une paroi périphérique 38 indépendante qui permet la circulation d’un flux d’air de dégivrage autour de chaque cellule 34.  Each cell 34 is delimited by an independent peripheral wall 38 which allows the circulation of a flow of defrosting air around each cell 34.
On entend par « paroi périphérique indépendante » que les cellules 34 adjacentes ne présentent pas de paroi commune, de sorte que l’air de dégivrage peut circuler tout autour de chaque cellule 34.  The term "independent peripheral wall" means that the adjacent cells 34 do not have a common wall, so that the defrosting air can circulate around each cell 34.
Comme on peut le voir à la figure 3, chaque cellule 34 présente une forme de dôme.  As can be seen in Figure 3, each cell 34 has a dome shape.
Plus particulièrement, selon l’exemple représenté à la figure 3, chaque cellule 34 présente une forme pyramidale, la paroi périphérique 38 de chaque cellule 34 formant quatre faces qui sont chacune en contact avec l’air de dégivrage qui circule dans la lèvre 24.  More particularly, according to the example shown in FIG. 3, each cell 34 has a pyramidal shape, the peripheral wall 38 of each cell 34 forming four faces which are each in contact with the deicing air flowing in the lip 24.
Toutefois, à titre non limitatif, chaque cellule 34 peut présenter une forme parallélépipédique, comme par exemple une forme carrée.  However, without limitation, each cell 34 may have a parallelepiped shape, such as a square shape.
En référence à la figure 3, les trois rangées 36 sont reliées entre elles deux à deux par deux portions de liaison 40 qui sont en appui sur la peau acoustique 33 de la lèvre 24 d’entrée d’air.  With reference to FIG. 3, the three rows 36 are interconnected two by two by two connecting portions 40 which bear on the acoustic skin 33 of the air intake lip 24.
Chaque portion de liaison 40 est une bande qui s’étend longitudinalement en largeur et qui épouse la forme de la lèvre 24.  Each connecting portion 40 is a band that extends longitudinally in width and which matches the shape of the lip 24.
Les cellules 34 adjacentes à chaque portion de liaison 40 forment une vallée dans laquelle l’air de dégivrage s’écoule pour transmettre des calories à la peau acoustique 33 par conduction, par l’intermédiaire de la structure acoustique 32 et particulièrement par l’intermédiaire des portions de liaison 40.  The cells 34 adjacent to each connecting portion 40 form a valley in which the defrosting air flows to transmit heat to the acoustic skin 33 by conduction, via the acoustic structure 32 and particularly via connecting portions 40.
De plus, la forme en dôme de chaque cellule 34 est également adaptée pour que l’air de dégivrage circule longitudinalement entre les cellules 34, c'est-à-dire perpendiculairement aux portions de liaison 40. A titre non limitatif, la structure acoustique 32 peut également comporter des bandes de liaison (non représentées) qui s’étendent longitudinalement en longueur pour relier les cellules 34 entre elles. Cette caractéristique est particulièrement adaptée aux cellules 34 de forme parallélépipédique pour permettre d’écarter les cellules 34 et permettre à l’air de dégivrage de circuler longitudinalement entre les cellules 34. In addition, the dome shape of each cell 34 is also adapted so that the defrosting air circulates longitudinally between the cells 34, that is to say perpendicularly to the connecting portions 40. Without limitation, the acoustic structure 32 may also comprise connecting strips (not shown) which extend longitudinally in length to connect the cells 34 to each other. This characteristic is particularly suitable for parallelepiped-shaped cells 34 to allow the cells 34 to be moved aside and allow the defrosting air to flow longitudinally between the cells 34.
Toujours selon la figure 3, on notera que les cellules 34 sont réalisées venues de matière avec la portion de liaison 40 associée.  Still according to FIG. 3, it will be noted that the cells 34 are made integrally with the associated connecting portion 40.
Autrement dit, chaque cellule 34 et chaque portion de liaison 40 sont formées par la structure acoustique 32 en une pièce monolithique. De préférence, la structure acoustique 32 est réalisée par formage à froid par emboutissage d’une tôle métallique.  In other words, each cell 34 and each connecting portion 40 are formed by the acoustic structure 32 in a monolithic piece. Preferably, the acoustic structure 32 is made by cold forming by stamping a metal sheet.
Toutefois, à titre non limitatif, la structure acoustique 32 peut également être réalisée par formage par explosion, par formage incrémental, par magnétoformage, ou encore par formage à chaud.  However, without limitation, the acoustic structure 32 can also be achieved by explosion-forming, by incremental forming, by magnetoforming, or by hot forming.
Aussi, la structure acoustique 32 est de préférence réalisée en plusieurs secteurs angulaires.  Also, the acoustic structure 32 is preferably made of several angular sectors.
De plus, la structure acoustique 32 est rapportée et fixée sur la peau acoustique 33 perforée, par exemple par brasage. La tôle qui sert à fabriquer la structure acoustique 32 peut être co-laminée avec un alliage de brasure pour supprimer l’étape de dépose de la brasure sur la structure acoustique 32.  In addition, the acoustic structure 32 is reported and fixed on the acoustic skin 33 perforated, for example by brazing. The sheet used to manufacture the acoustic structure 32 may be co-laminated with a solder alloy to eliminate the step of depositing the solder on the acoustic structure 32.
A titre non limitatif, la structure acoustique 32 peut également être fixée par soudage.  Without limitation, the acoustic structure 32 can also be fixed by welding.
Les trous 41 formés dans la peau acoustique 33 qui sont agencés au droit des portions de liaison 40 sont bouchés par les portions de liaison acoustique 40 et les trous 41 qui sont agencés au droit des cellules 34 sont ouverts et débouchent dans les cellules 34.  The holes 41 formed in the acoustic skin 33 which are arranged at the right of the connecting portions 40 are plugged by the acoustic connection portions 40 and the holes 41 which are arranged in line with the cells 34 are open and open into the cells 34.
Selon un autre aspect de l’invention, le dispositif 10 comporte un tube 42 de distribution de l’air de dégivrage illustré aux figures 2, 7 et 8, qui présente une forme torique autour de l’axe A central et qui est agencé dans la lèvre 24.  According to another aspect of the invention, the device 10 comprises a defrost air distribution tube 42 illustrated in FIGS. 2, 7 and 8, which has a toric shape around the central axis A and which is arranged in the lip 24.
Le tube 42 comporte une entrée (non représentée) qui est reliée à une source d’air chaud de dégivrage et une sortie (non représentée).  The tube 42 has an inlet (not shown) which is connected to a defrost hot air source and an outlet (not shown).
De plus, le tube 42 délimite une pluralité de fentes 44 formant injecteurs, qui sont agencées en regard des cellules 34 et qui dirigent l’air de dégivrage entre les cellules 34, de sorte que l’air de dégivrage passe autour de chaque cellule 34 comme on peut le voir aux figures 7 et 8. In addition, the tube 42 defines a plurality of injector slots 44, which are arranged facing the cells 34 and which direct the air defrosting between the cells 34, so that the defrosting air passes around each cell 34 as can be seen in FIGS. 7 and 8.
Selon une première variante de réalisation illustrée à la figure 4, le dispositif 10 comporte une pluralité de déflecteurs 46 qui remplacent le tube 42 de distribution d’air de dégivrage et qui sont agencés angulairement de façon régulière autour de l’axe A central.  According to a first embodiment shown in Figure 4, the device 10 comprises a plurality of deflectors 46 which replace the defrosting air distribution tube 42 and which are angularly arranged in a regular manner around the central axis A.
Selon cette première variante, l’air de dégivrage est injecté dans la lèvre 24 par une buse 48 qui imprime un mouvement circulaire à l’air de dégivrage, autour de l’axe A central.  According to this first variant, the defrosting air is injected into the lip 24 by a nozzle 48 which prints a circular motion to the defrosting air around the central axis A.
De plus, chaque déflecteur 46 chapeaute la structure acoustique 32 et s’étend globalement tangentiellement par rapport à l’axe A central, et chaque déflecteur 46 présente un bord d’attaque 50 qui est sensiblement relevé pour diriger une partie du flux d’air de dégivrage vers les cellules 34 pour favoriser les échanges thermiques.  In addition, each deflector 46 covers the acoustic structure 32 and extends generally tangentially with respect to the central axis A, and each deflector 46 has a leading edge 50 which is substantially raised to direct a portion of the air flow defrosting to the cells 34 to promote heat exchange.
Selon une seconde variante de réalisation illustrée aux figures 5 et 6, le dispositif 10 comporte un déflecteur 52 annulaire qui s’étend autour de l’axe A central et qui chapeaute la structure acoustique 32.  According to a second variant embodiment illustrated in FIGS. 5 and 6, the device 10 comprises an annular baffle 52 which extends around the central axis A and which surrounds the acoustic structure 32.
En référence à la figure 6, l’air de dégivrage est injecté dans la lèvre 32 par un une entrée 54 qui est ménagée dans la cloison aval 28, de sorte que l’air de dégivrage tourbillonne dans la lèvre 24 comme illustré par la flèche sur la figure 6.  With reference to FIG. 6, the defrosting air is injected into the lip 32 via an inlet 54 which is formed in the downstream partition 28, so that the defrosting air swirls in the lip 24 as illustrated by the arrow in Figure 6.
Le déflecteur 52 est recourbé à ses deux extrémités pour que le flux d’air de dégivrage tourbillonnant passe entre le déflecteur 52 et les cellules 34, pour favoriser les échanges thermiques.  The deflector 52 is bent at both ends so that the flow of swirling defrost air passes between the deflector 52 and the cells 34, to promote heat exchange.
L’invention concerne également un procédé de fabrication d’un dispositif 10 de dégivrage et de traitement acoustique du type décrit précédemment, qui comprend une étape de fabrication qui consiste à réaliser les rangées 36 de cellules 34 acoustiques et les portions de liaison 40 associées venues de matière.  The invention also relates to a method of manufacturing a device 10 for deicing and acoustic treatment of the type described above, which comprises a manufacturing step which consists in producing the rows 36 of acoustic cells 34 and the associated connecting portions 40 of matter.
La présente description de l’invention est donnée à titre d’exemple non limitatif.  The present description of the invention is given by way of non-limiting example.

Claims

REVENDICATIONS
1 . Dispositif (30) de dégivrage et de traitement acoustique pour une lèvre (24) d’entrée d’air d’une nacelle (10) de turboréacteur, caractérisé en ce qu’il comporte une structure acoustique (32) gaufrée qui est adaptée pour être en appui sur une peau acoustique (33) de la lèvre (24) d’entrée d’air, et qui délimite une pluralité de cellules (34) acoustiques, chaque cellule (34) étant délimitée par une paroi périphérique (38) indépendante qui permet la circulation d’un flux d’air de dégivrage autour de chaque cellule (34). 1. Device (30) for deicing and acoustic treatment for an air inlet lip (24) of a turbojet engine nacelle (10), characterized in that it comprises an embossed acoustic structure (32) which is adapted to resting on an acoustic skin (33) of the air intake lip (24), which delimits a plurality of acoustic cells (34), each cell (34) being delimited by an independent peripheral wall (38) which allows the circulation of a flow of defrosting air around each cell (34).
2. Dispositif (30) de dégivrage et de traitement acoustique selon la revendication 1 , caractérisé en ce que la structure acoustique (32) délimite au moins deux rangées (36) de cellules (34) qui sont reliées entre elles par au moins une portion de liaison (40) adaptée pour être en appui sur la peau acoustique (33) de la lèvre (24) d’entrée d’air.  2. Device (30) for deicing and acoustic treatment according to claim 1, characterized in that the acoustic structure (32) defines at least two rows (36) of cells (34) which are interconnected by at least one portion link (40) adapted to bear on the acoustic skin (33) of the lip (24) of air inlet.
3. Dispositif (30) de dégivrage et de traitement acoustique selon la revendication 2, caractérisé en ce que les cellules (34) sont réalisées venues de matière avec la portion de liaison (40) associée.  3. Device (30) for deicing and acoustic treatment according to claim 2, characterized in that the cells (34) are made integrally with the connecting portion (40) associated.
4. Dispositif (30) de dégivrage et de traitement acoustique selon l’une quelconque des revendications 2 et 3, caractérisé en ce que chaque rangée (36) de cellules (34) acoustiques présente une forme annulaire autour d’un axe (A) central.  4. Device (30) for deicing and acoustic treatment according to any one of claims 2 and 3, characterized in that each row (36) of cells (34) acoustic has an annular shape about an axis (A) central.
5. Dispositif (30) de dégivrage et de traitement acoustique selon l’une quelconque des revendications précédentes, caractérisé en ce que la structure acoustique (32) présente une forme annulaire monolithique ou une forme de plusieurs secteurs angulaires monolithiques.  5. Device (30) for deicing and acoustic treatment according to any one of the preceding claims, characterized in that the acoustic structure (32) has a monolithic annular shape or a shape of several monolithic angular sectors.
6. Dispositif (30) de dégivrage et de traitement acoustique selon l’une quelconque des revendications précédentes, caractérisé en ce que chaque cellule (34) présente une forme globalement pyramidale.  6. Device (30) for deicing and acoustic treatment according to any one of the preceding claims, characterized in that each cell (34) has a generally pyramidal shape.
7. Dispositif (30) de dégivrage et de traitement acoustique selon l’une quelconque des revendications précédentes, caractérisé en ce qu’il comporte au moins un déflecteur (46, 52) qui est conçu pour guider un flux d’air de dégivrage vers la structure acoustique (32).  7. Device (30) for deicing and acoustic treatment according to any one of the preceding claims, characterized in that it comprises at least one deflector (46, 52) which is designed to guide a flow of defrost air to the acoustic structure (32).
8. Dispositif (30) de dégivrage et de traitement acoustique selon l’une quelconque des revendications 1 à 6, caractérisé en ce qu’il comporte un tube (42) de distribution de l’air de dégivrage qui présente une forme torique autour de l’axe (A) et qui délimite une pluralité de fentes (44) formant injecteurs, les fentes étant agencées en regard des cellules (34) pour diriger l’air de dégivrage entre les cellules (34). 8. Device (30) of defrosting and acoustic treatment according to any one of claims 1 to 6, characterized in that it comprises a tube (42) of defrost air distribution which has a toroidal shape around the axis (A) and which delimits a plurality of slots (44) forming injectors, the slots being arranged facing the cells (34) to direct deicing air between the cells (34).
9. Procédé de fabrication d’un dispositif (30) de dégivrage et de traitement acoustique pour une lèvre (24) d’entrée d’air d’une nacelle (10) de turboréacteur, dispositif (30) qui comporte une structure acoustique (32) gaufrée qui délimite une pluralité de cellules (34) acoustiques, chaque cellule (34) étant délimitée par une paroi périphérique (38) indépendante qui permet la circulation d’un flux d’air de dégivrage autour de chaque cellule (34), caractérisé en ce qu’il comprend au moins une étape de fabrication qui consiste à réaliser la structure acoustique (32) venue de matière en une pièce monolithique.  9. A method of manufacturing a device (30) for deicing and acoustic treatment for an air inlet lip (24) of a turbojet engine nacelle (10), a device (30) comprising an acoustic structure ( 32) which delimits a plurality of acoustic cells (34), each cell (34) being delimited by an independent peripheral wall (38) which allows a flow of defrost air to circulate around each cell (34), characterized in that it comprises at least one manufacturing step which consists in producing the acoustic structure (32) made of material in a monolithic piece.
10. Nacelle (10) de turboréacteur du type comportant un dispositif (30) de dégivrage et de traitement acoustique selon l’une quelconque des revendications 1 à 8.  10. Nacelle (10) turbojet engine of the type comprising a device (30) for deicing and acoustic treatment according to any one of claims 1 to 8.
EP19710043.1A 2018-02-12 2019-02-08 De-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle Active EP3752420B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1851152A FR3077800B1 (en) 2018-02-12 2018-02-12 DEFROSTING AND ACOUSTIC TREATMENT DEVICE FOR AN AIR INLET LIP OF A TURBOREACTOR NACELLE
PCT/FR2019/050286 WO2019155175A1 (en) 2018-02-12 2019-02-08 De-icing and acoustic treatment device for an air intake lip of a turbojet engine nacelle

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FR2820715B1 (en) * 2001-02-15 2003-05-30 Eads Airbus Sa PROCESS FOR DEFROSTING AN AIR INTAKE COVER OF A REACTION ENGINE AND DEVICE FOR IMPLEMENTING SAME
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FR3077800B1 (en) 2020-09-25
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EP3752420B1 (en) 2024-05-29
WO2019155175A1 (en) 2019-08-15

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